DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 [58 FR 67307 NO. 243 12/21/93]

[Docket No. 93-ANE-50; Amendment 39-8704; AD 93-16-14]

Airworthiness Directives; Hartzell Propeller Inc. HC-()3Y()-() Series Three-Bladed Propellers

AGENCY:  Federal Aviation Administration, DOT. 

ACTION:  Final rule, request for comments.

SUMMARY:  This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 93-16-14 that was sent previously to all known U.S. owners and operators of Hartzell Propeller Inc. HC-()3Y()-() series three-bladed propellers by individual letters.  This AD requires initial and repetitive visual inspections and eddy current inspections for cracks in the area of the grease fitting holes on the side of the propeller hub.  This amendment is prompted by propeller hub failure on a propeller that had been visually inspected in accordance with priority letter AD 89-22-05.  The actions specified by this AD are intended to prevent propeller hub failure and subsequent propeller blade separation and loss of the aircraft. 

DATES:  Effective January 5, 1994, to all persons except those persons to whom it was made immediately effective by priority letter AD 93-16-14, issued on August 18, 1993, which contained the requirements of this amendment.

	The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of January 5, 1994.

	Comments for inclusion in the Rules Docket must be received on or before February 22, 1994.

ADDRESSES:  Submit comments in triplicate to the Federal Aviation Administration (FAA), New England Region, Office of the Assistant Chief Counsel, Attention:  Rules Docket No. 93-ANE-50, 12 New England Executive Park, Burlington, MA 01803-5299.

	The applicable service information may be obtained from Hartzell Propeller Inc., One Propeller Place, Piqua, OH 45356-2834; fax (513) 778-4391.  This information may be examined at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. 

FOR FURTHER INFORMATION CONTACT:  Tim Smyth, Aerospace  Engineer, Chicago Aircraft Certification Office, FAA, Small  Airplane Directorate, 2300 East Devon Avenue, Room 232, Des  Plaines, IL 60018; telephone (708) 294-7130, fax   (708) 294-7834. 

SUPPLEMENTARY INFORMATION:  On October 20, 1989, the Federal Aviation Administration (FAA) issued priority letter AD 89-22-05, applicable to Hartzell Propeller Inc. HC-()3Y()-() series three-bladed propellers, which requires visual inspection of the propeller hub surface in the area of the grease fittings at intervals of 50 hours time in service (TIS).  That action was prompted by reports of propeller hub failures caused by cracks initiating in the grease fitting holes on the side of the hub.  These cracks typically originate in the threads of the hub grease fitting, then propagate around the blade arm of the hub, resulting in failure of one hub half.  That condition, if not corrected, could result in propeller hub failure and subsequent propeller blade separation and loss of the aircraft.  

	Since the issuance of that AD, the FAA has received a report from the Civil Aviation Authority (CAA) of Great Britain of a propeller hub failure on a propeller that had been visually inspected in accordance with the current AD.  The CAA's investigation revealed that the propeller hub crack had corrosion on the fracture surface that was present for a considerable time but the crack was undetectable by visual inspection.  The FAA, in conjunction with the CAA and the manufacturer, has determined that the visual inspection procedure alone is inadequate to reliably find cracks in the propeller hub.  On August 18, 1993, the FAA issued priority letter AD 93-16-14, which requires initial and repetitive visual inspections and eddy current inspections (ECI) for cracks in the area of the grease fitting holes on the side of the propeller hub.

	The FAA has reviewed and approved the technical contents of Hartzell Propeller Inc. Service Bulletin (SB) No. 165D, dated August 6, 1993, that describes procedures for visual inspections and ECI for cracks in the area of the grease fitting holes on the side of the propeller hub.

	Since an unsafe condition has been identified that is likely to exist or develop on other propellers of this same type design, this AD supersedes priority letter AD 89-22-05, and requires initial and repetitive visual inspections and ECI for cracks in the area of the grease fitting holes on the side of the propeller hub.  If a propeller hub is found cracked, the hub must be replaced prior to further flight with a post-1983 later style propeller hub, or with a serviceable 1983 or earlier hub that has been inspected in accordance with Hartzell Propeller Inc. SB No. 165D, dated August 6, 1993.  Affected propeller installations that have experienced failures in service are required to have a repetitive visual inspection and ECI every 25 hours TIS.  Other aircraft models utilizing the affected propellers which have not had a failure in service but have similar installation designs and operational characteristics are required to have a repetitive visual inspection and ECI every 50 hours TIS.  The FAA has determined that those propeller hubs removed from service in accordance with this AD which are not cracked may not be reinstalled on any aircraft exempt from this AD.  Cumulative fatigue damage may have occurred that is not yet detectable.  The repetitive inspections required by this AD on affected aircraft installations provides for detecting fatigue damage that grows to a crack.

	This AD is an interim action.  The FAA may consider future rulemaking that requires installation of a post-1983, later style propeller hubs which have relocated the grease fitting holes near the hub parting line.

	Since it was found that immediate corrective action was required, notice and opportunity for prior public comment thereon were impracticable and contrary to the public interest, and good cause existed to make the AD effective immediately by individual letters issued on August 18, 1993, to all known U.S. owners and operators of Hartzell Propeller Inc. HC-()3Y()-() series three-bladed propellers.  These conditions still exist, and the AD is hereby published in the Federal Register as an amendment to Section 39.13 of part 39 of the Federal Aviation Regulations (FAR) to make it effective to all persons.

Comments Invited

	Although this action is in the form of a final rule that involves requirements affecting flight safety and, thus, was not preceded by notice and an opportunity for public comment, comments are invited on this rule.  Interested persons are invited to comment on this rule by submitting such written data, views, or arguments as they may desire.  Communications should identify the Rules Docket number and be submitted in triplicate to the address specified under the caption "ADDRESSES."  All communications received on or before the closing date for comments will be considered, and this rule may be amended in light of the comments received.  Factual information that supports the commenter's ideas and suggestions is extremely helpful in evaluating the effectiveness of the AD action and determining whether additional rulemaking action would be needed.

	Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify the rule.  All comments submitted will be available, both before and after the closing date for comments, in the Rules Docket for examination by interested persons.  A report that summarizes each FAA-public contact concerned with the substance of this AD will be filed in the Rules Docket.

	Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this notice must submit a self-addressed, stamped postcard on which the following statement is made:  "Comments to Docket Number 93-ANE-50."  The postcard will be date stamped and returned to the commenter.

	The regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.  Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment.

	The FAA has determined that this regulation is an emergency regulation and that it is not considered to be major under Executive Order 12291.  It is impracticable for the agency to follow the procedures of Order 12291 with respect to this rule since the rule must be issued immediately to correct an unsafe condition in aircraft.  It has been determined further that this action involves an emergency regulation under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979).  If it is determined that this emergency regulation otherwise would be significant under DOT Regulatory Policies and Procedures, a final regulatory evaluation will be prepared and placed in the Rules Docket.  A copy of it, if filed, may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES."

List of Subjects in 14 CFR Part 39

	Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

Adoption of the Amendment 
	Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends 14 CFR part 39 of the Federal Aviation Regulations as follows: 

PART 39 - AIRWORTHINESS DIRECTIVES

	1.	The authority citation for part 39 continues to read as follows: 

Authority:  49 U.S.C. App. 1354(a), 1421 and 1423;  49 U.S.C. 106(g); and 14 CFR 11.89. 

§ 39.13 - [AMENDED]

	2.	Section 39.13 is amended by adding the following new airworthiness directive:

93-16-14  Hartzell Propeller Inc.:  Amendment 39-8704.  Docket 93-ANE-50.  Supersedes priority letter AD 89-22-05.

	Applicability:  Hartzell Propeller Inc. HC-()3Y()-() series three-bladed propellers with model designations and serial number ranges listed as follows:  

Propeller Basic 
Hub Model					Propeller Serial Number Range

PHC-C3YF-1R()				EE1 through EE1461
PHC-J3YF-1R()				FP1 through FP37
PHC-L3YF-1R()				FD1 through FD7
HC-C3YF-1R()				EC1 through EC1020
HC-C3YK-1R() or HC-C3YR-1R()		DY1 through DY1897
HC-C3YK-1()					CT1 through CT101
HC-C3YK-2() or HC-C3YR-2()		CK1 through CK3510
HC-C3YK-4() or HC-C3YR-4()		EL1 through EL67
HC-E3YK-1() or HC-E3YR-1()		FM1 through FM487
HC-E3YK-2() or HC-E3YR-2()		DF1 through DF79
HC-E3YK-2A() or HC-E3YR-2A()		DJ1 through DJ7787
HC-F3YK-2() or HC-F3YR-2()		DA1 through DA1586
HC-F3YK-1() or HC-F3YR-1()		DB1 through DB137
HC-I3YK-2() or HC-I3YR-2()		FS1 through FS32 
 	
	This AD applies to the above affected propellers when installed on any agricultural aircraft with any engine, or installed on any aircraft utilizing Textron Lycoming (L)TIO-540 series piston engines, or IO-540 series piston engines that have a turbocharger added by the airframe manufacturer or have been modified by a Supplemental Type Certificate (STC) to incorporate a turbocharger.  The known affected propellers are installed on, but not limited to the following aircraft: 

AGRICULTURAL AIRCRAFT:

Fletcher FU24-950
Cessna A188 Agwagon modified by STC SA895SO
Piper PA-36-300 Pawnee
PA-36 Pawnee modified by STC SA3952WE
Transavia Airtruk Models and PL-12/T-300 Skyfarmer
 
AIRCRAFT WITH TEXTRON LYCOMING (L)TIO-540 and TURBOCHARGED
IO-540 SERIES ENGINES:

Cessna 310 and 320 modified by Riley STC SA2082WE
Gulfstream 700 (formerly Rockwell 700, Fuji FA-300-12)
Helio H-700
Piper PA-23-250 and PA-E23-250 (with TIO-540 only)
Piper PA-31 Navajo (with TIO-540 only)
Piper PA-31-325 Navajo C/R
Piper PA-31-350 Navajo "Chieftain"
Piper PA-31P-350 Mohave
Piper T-1020 (same as PA-31-350)
Piper PA-32(R)-301T Turbo Saratoga
Piper PA-60-600, PA-60-601, and PA-60-602 Aerostar's all modified by Machen STC (turbocharged)
Piper PA-60-700P Aerostar 700P

	Propellers with model designations and serial number ranges listed above and installed on non-agricultural aircraft, which do NOT utilize Textron Lycoming (L)TIO-540 or turbocharged IO-540 series engines are exempt from this AD.
	Propellers with post-1983 hub configurations, i.e., which have the relocated grease fitting holes near the hub parting line as shown in Figure 1, page 8, of Hartzell Propeller, Inc., Service Bulletin (SB) No. 165D, dated August 6, 1993, even though the propeller model and serial number are listed above, are exempt from this AD.
	Compliance:  Required as indicated, unless accomplished previously.
	To prevent propeller hub failure due to cracks that originate in the grease fitting holes on the side of the hub, which could result in propeller blade separation and loss of the aircraft, accomplish the following: 
	(a)	For propellers installed on Textron Lycoming (L)TIO-540 series piston engines or turbocharged IO-540 series piston engines which are installed on Piper PA-31-325 Navajo C/R, PA-31-350 Navajo "Chieftain," T-1020 (same as PA-31-350), PA-60-700P, Aerostar 700P aircraft, or propellers installed on any agricultural aircraft with any engine, accomplish the following:
		(1)	Within 25 hours time in service (TIS) after  the effective date of this AD, and thereafter at intervals of 25 hours TIS, perform a visual inspection and eddy current inspection (ECI) for cracks in accordance with Hartzell Propeller Inc. SB No. 165D, dated August 6, 1993.
		(2)	If a crack is found in a propeller hub during the inspections required in paragraph (a)(1) of this AD, replace the hub prior to further flight with a post-1983 later style propeller hub, or with a serviceable 1983 or earlier hub that has been inspected in accordance with Hartzell Propeller Inc. SB No. 165D, dated August 6, 1993.  Thereafter, perform a visual inspection and ECI for cracks in accordance with Hartzell Propeller Inc. SB No. 165D, dated August 6, 1993, at intervals not to exceed 25 hours TIS since the last inspection, unless a post-1983 later style propeller hub is installed, per paragraph (d) of this AD.
	(b)	For propellers installed on all other aircraft models, except for the four non-agricultural models listed in paragraph (a) of this AD, and that utilize Textron Lycoming (L)TIO-540 or turbocharged IO-540 series piston engines accomplish the following:
		(1)	Within 50 hours TIS after the effective date of this AD this AD, and thereafter at intervals of 50 hours TIS, perform a visual inspection and ECI for cracks in accordance with Hartzell Propeller Inc. SB No. 165D, dated August 6, 1993.
		(2)	If a crack is found in a propeller hub during the inspections required in paragraph (b)(1) of this AD, replace the hub prior to further flight with a post-1983 later style propeller hub, or with a serviceable 1983 or earlier hub that has been inspected in accordance with Hartzell Propeller Inc. SB No. 165D, dated August 6, 1993.  Thereafter, perform a visual inspection and ECI for cracks in accordance with Hartzell Propeller Inc. SB No. 165D, dated August 6, 1993, at intervals not to exceed 50 hours TIS since the last inspection, unless a post-1983 later style propeller hub is installed, per paragraph (d) of this AD.
	(c)	Propeller hubs that are 1983 or earlier, with the grease fitting holes located on the side of the hub, that have been removed from service cannot be returned to service on aircraft that are exempt from this AD.
	(d)	Installation of post-1983 later style propeller hubs that have relocated grease fitting holes near the hub parting line constitutes terminating action to the inspection requirements of this AD.
	(e)	An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Chicago Aircraft Certification Office.  The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Chicago Aircraft Certification Office.
	NOTE:  Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Chicago Aircraft Certification Office.
	(f)	Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the aircraft to a location where the requirements of this AD can be accomplished.
	(g)	The inspections, and replacement, if necessary, shall be done in accordance with the following Hartzell Propeller Inc. service bulletin: 

Document No.		Pages		Date

165D 				1-8		August 6, 1993
Total pages:  8.

This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.  Copies may be obtained from Hartzell Propeller Inc., One Propeller Place, Piqua, OH 45356-2834; fax (513) 778-4391.  Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. 
	(h)	This action supersedes priority letter AD 89-22-05, issued October 20, 1989.
	(i)	This amendment becomes effective January 5, 1994, to all persons except those persons to whom it was made immediately effective by priority letter AD 93-16-14, issued August 18, 1993, which contained the requirements of this amendment. 

FOR FURTHER INFORMATION CONTACT:  Tim Smyth, Aerospace  Engineer, Chicago Aircraft Certification Office, FAA, Small  Airplane Directorate, 2300 East Devon Avenue, Room 232, Des  Plaines, IL 60018; telephone (708) 294-7130, fax   (708) 294-7834.